Atlas III
Atlas III
Space Launch Systems
Basic Information
Name
Atlas III
Designation
Atlas III
Alternate Designation
Atlas IIIA, Atlas IIIB
Equipment Type
Space Launch Systems
Manufacturer
Lockheed Martin
Date of Introduction
2000
Description
The Atlas III family comprises the Atlas IIIA and Atlas IIIB models. The main difference between the Atlas III space launch system and its predecessor, the Atlas II, is the RD-180 rocket engine which enables Atlas III to lift payloads of 9,920-pound (4500 kg) to GTO. The sixth and final Atlas III launch vehicle flew from Cape Canaveral, Florida, on February 2, 2005. The last Atlas III placed into orbit a national security payload for the US National Reconnaissance Office marking the 75 consecutive successful mission for the Atlas vehicle. Atlas III was developed to fill between the capabilities of Atlas II and the most capable Atlas V.
Overview (Deagel)
Group
Space Launch Systems
Status
Retired - No Longer Operational
Also Known As
Atlas IIIA, Atlas IIIB
Origin
United States of America
Contractor
Lockheed Martin
Initial Operational Capability (IOC)
2000
Total Production
6
Specifications (Deagel)
Crew
0
Dimensions — Height
53.1 meter
Dimensions — Rocket Diameter
3.0 meter
Mass — Max Lift-off Thrust
860,200 pound
Mass — Max Lift-off Weight
224 ton
Mass — Payload to GTO
9,920 pound
Gear (Deagel)
Item 1
Rocket Engines: RD-180 (1)
Variants
Variant 1
Atlas II
Variant 2
Atlas III
Variant 3
Atlas V
Details
Country of Origin
United States
Sources
deagel.com: https://www.deagel.com/x/x/a000237
Classification
Domain
Air & Air Defense
Equipment Status
Active
Dimensions
Length
—
Width
3 m
Height
53.1 m
Weight
224000 kg
Operators (1)
United States
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